Acoustic transducer in system for gas temperature measurement in gas turbine engine

• US 9,696,216 B2
• Filed: 03/05/2015
• Issued: 07/04/2017
• Est. Priority Date: 09/04/2013
• Status: Expired due to Fees

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: DeSilva, Upul P., Claussen, Heiko
• Primary Examiner(s): Gibson, Randy
• Application Number:
  US14/639,563
• Publication Number:
  US 20150185089A1
• Time in Patent Office: 852 Days
• CPC Class Codes: F02C 9/00 Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05
• CPC Class Codes: F05D 2270/303 Temperature
• CPC Class Codes: G01H 1/003 of rotating machines G01H1/10 takes precedence
• CPC Class Codes: G01H 3/00 Measuring characteristics of vibrations by using a detector in a fluid G01H7/00, G01H9/00, G01H11/00 take precedence
• CPC Class Codes: G01K 11/24 of the velocity of propagation of sound
• CPC Class Codes: G01K 13/02 for measuring temperature of moving fluids or granular materials capable of flow
• CPC Class Codes: G01K 13/024 of moving gases
• CPC Class Codes: G01M 15/14 Testing gas-turbine engines or jet-propulsion engines

Abstract

An apparatus for controlling operation of a gas turbine engine including at least one acoustic transmitter/receiver device located on a flow path boundary structure. The acoustic transmitter/receiver device includes an elongated sound passage defined by a surface of revolution having opposing first and second ends and a central axis extending between the first and second ends, an acoustic sound source located at the first end, and an acoustic receiver located within the sound passage between the first and second ends. The boundary structure includes an opening extending from outside the boundary structure to the flow path, and the second end of the surface of revolution is affixed to the boundary structure at the opening for passage of acoustic signals between the sound passage and the flow path.

Claims

1. A gas turbine engine including an apparatus for controlling operation of the gas turbine engine, and the engine having a boundary structure defining a flow path passing through the engine, the apparatus for controlling operation of the engine comprising:

at least one acoustic transmitter/receiver device located on the boundary structure at a predetermined axial location along the flow path, the acoustic transmitter/receiver device including;

an elongated sound passage defined by a surface of revolution having opposing first and second ends and a central axis extending between the first and second ends;

an acoustic sound source located at the first end; and

an acoustic receiver located within the sound passage between the first and second ends;

the boundary structure including an opening extending from outside the boundary structure to the flow path; and

the second end of the surface of revolution is affixed to the boundary structure at the opening for passage of acoustic signals between the sound passage and the flow path.

2. The gas turbine engine of claim 1, wherein the acoustic receiver includes a support rod extending through a hole in the surface of revolution between the first and second ends, the support rod having an inner end located within the sound passage and supporting a receiver end for receiving acoustic signals into the acoustic receiver.

3. The gas turbine engine of claim 2, wherein the acoustic receiver includes a microphone located on the inner end of the support rod and defining the receiver end.

4. The gas turbine engine of claim 3, wherein the support rod is detachably affixed to the surface of revolution, and is supported for movement of the inner end toward and away from the central axis of the surface of revolution.

5. The gas turbine engine of claim 3, wherein the support rod includes a central portion defining a rod axis extending through the hole in the surface of revolution and transverse to the central axis, and the support rod includes a transition portion that is bent to position a sound receiving opening of the microphone facing away from the acoustic source and toward the flow path.

6. The gas turbine engine of claim 3, wherein the microphone is located at the central axis of the surface of revolution.

7. The gas turbine engine of claim 3, including a preamplifier receiving acoustic signals from the microphone and located at an outer end of the support rod outside of the sound passage.

8. The gas turbine engine of claim 2, wherein the receiver end at the inner end of the support rod is formed as a horn defined by an outwardly tapered wall, extending from the inner end of the support rod, for receiving acoustic signals into the acoustic receiver.

9. The gas turbine engine of claim 8, wherein the support rod includes a hollow central portion defining a waveguide extending through the hole in the surface of revolution, and the acoustic receiver including a microphone at an outer end of the support rod outside of the sound passage.

10. The gas turbine engine of claim 8, wherein the surface of revolution is tapered outwardly from the acoustic source to the boundary structure and defines a horn surrounding the horn of the receiver end.

11. The gas turbine engine of claim 10, wherein the horn of the receiver end includes an open end located at the opening of the boundary structure, and an annular acoustic transmission passage is defined between the surface of revolution and the horn of the receiver at the boundary structure.

12. The gas turbine engine of claim 8, wherein the first end of the surface of revolution defines a parabolic dish surface facing toward the horn of the receiver end, and the horn of the receiver end includes an open end facing toward the parabolic dish surface.

13. The gas turbine engine of claim 12, wherein the acoustic sound source is spaced from the parabolic dish surface by an elongated waveguide having a proximal outlet opening adjacent to the parabolic dish surface and a distal inlet opening adjacent to the acoustic sound source.

14. The gas turbine engine of claim 1, wherein the central axis of the acoustic transmitter/receiver device is oriented at an angle between 90 degrees and 180 degrees relative to an axial flow direction of gases in the flow path to project acoustic signals in a downstream direction from the opening in the boundary structure.

15. The gas turbine engine of claim 14, wherein the at least one acoustic transmitter/receiver device defines a first acoustic transmitter/receiver device, and including a second acoustic transmitter/receiver device located on the boundary structure at a predetermined axial position in a downstream direction from the first acoustic transmitter/receiver device relative to a gas flow direction in the flow path, the second transmitter/receiver device receiving acoustic sound signals transmitted from the first acoustic transmitter/receiver device.

16. A gas turbine engine including an apparatus for controlling operation of the gas turbine engine, and the engine having a boundary structure defining a flow path passing through the engine, the apparatus for controlling operation of the engine comprising:

first and second acoustic transmitter/receiver devices located on the boundary structure at predetermined axial locations along the flow path, the acoustic transmitter/receiver devices each including;

an elongated sound passage defined by a surface of revolution having opposing first and second ends and a central axis extending between the first and second ends;

an acoustic sound source located at the first end; and

an acoustic receiver located within the sound passage between the first and second ends, the acoustic receiver including a support rod extending through a hole in the surface of revolution between the first and second ends, the support rod having an inner end located within the sound passage and supporting a receiver end for receiving acoustic signals into the acoustic receiver;

the boundary structure including first and second openings extending from outside the boundary structure to the flow path; and

the second end of each surface of revolution is affixed to the boundary structure at a respective one of the openings for passage of acoustic signals between the sound passage and the flow path.

17. The gas turbine engine of claim 16, wherein the central axes of the surface of revolution for the first and second acoustic transmitter/receiver devices are located on a common line passing through the flow path and oriented at a non-perpendicular direction relative to the flow path direction.

18. A gas turbine engine including an apparatus for controlling operation of the gas turbine engine, and the engine having a boundary structure defining a flow path passing through the engine, the apparatus for controlling operation of the engine comprising:

first and second acoustic transmitter/receiver devices located on the boundary structure at predetermined axial locations along the flow path, the acoustic transmitter/receiver devices each including;

an elongated sound passage defined by a surface of revolution having opposing first and second ends and a central axis extending between the first and second ends;

an acoustic sound source located at the first end; and

an acoustic receiver located within the sound passage between the first and second ends;

the boundary structure including first and second openings extending from outside the boundary structure to the flow path;

the second end of each surface of revolution is affixed to the boundary structure at a respective one of the openings for passage of acoustic signals between the sound passage and the flow path;

a signal generator producing at least one signal having a distinct signature defined by a set of predetermined frequencies forming a non-broadband signal that is output as an acoustic sound signal at the acoustic sound source;

a signal processor configured to compare signals received at the second acoustic transmitter/receiver device to one or more transmitted signals to identify a similarity of a received signal to a transmitted signal to identify a transmission time for the received signal, and the processor configured to determine a time-of-flight for the received signal and to process the time-of-flight to determine a temperature in a region of the predetermined axial location.

19. The gas turbine engine of claim 18, wherein the acoustic receiver of the first acoustic transmitter/receiver device includes a microphone connected to the signal processor and providing a signal corresponding to initiation of the transmitted signal as the transmitted signal passes the acoustic receiver of the first acoustic transmitter/receiver device.